Adaptive landing gear assembly for rotary wing aircraft

Patent metadata

Field	Value
Publication number	US-10689098-B2
Application number	US-201615580204-A
Country	US
Kind code	B2
Filing date	Jun 24, 2016
Priority date	Jun 25, 2015
Publication date	Jun 23, 2020
Grant date	Jun 23, 2020

Abstract

An adaptive landing gear assembly for a rotary wing aircraft, the adaptive landing gear assembly including a controller; a first landing gear support having a first ground contact element; and a second landing gear support having a second ground contact element; the controller independently controlling the first landing gear support and the second landing gear support.

First claim

What is claimed is:

1. An adaptive landing gear assembly for a rotary wing aircraft, the adaptive landing gear assembly comprising:
a controller;
a first landing gear support having a first ground contact element; and
a second landing gear support having a second ground contact element;
a sensor to monitor at least one condition of the aircraft; and
the controller independently controlling the first landing gear support and the second landing gear support in response to the sensor;
wherein the sensor monitors oscillation in an airframe of the aircraft or in a rotor system of the aircraft and the controller independently controls the first landing gear support and the second landing gear support to actuate an airframe response or rotor system response that dampens oscillation in the airframe or the rotor system due to ground resonance.

2. The adaptive landing gear assembly of claim 1 , wherein:
the sensor monitors orientation of a ship deck; and
the controller independently controls the first landing gear support and the second landing gear support in response to the orientation of the ship deck.

3. The adaptive landing gear assembly of claim 1 , wherein:
the sensor monitors orientation of a sloped surface; and
the controller independently controls the first landing gear support and the second landing gear support in response to the orientation of the sloped surface.

4. The adaptive landing gear assembly of claim 1 , wherein:
the first landing gear support and the second landing gear support include fluid, the controller independently controlling fluid in the first landing gear support and fluid in the second landing gear support in response to the sensor.

5. The adaptive landing gear assembly of claim 4 , wherein:
the fluid is at least one of a liquid and a gas.

6. The adaptive landing gear assembly of claim 1 , further comprising:
a first retention assembly to secure the first landing gear support in a position between fully up and fully down, the first retention assembly comprising a first actuator to position the first landing gear support.

7. The adaptive landing gear assembly of claim 6 , further comprising:
a second retention assembly to secure the second landing gear support in a position between fully up and fully down, the second retention assembly comprising a second actuator to position the second landing gear support.

8. The adaptive landing gear assembly of claim 7 , further comprising:
a ground contact member extension stop configured to relieve compressive loads experienced by the first or second actuator when the associated landing gear support is in a fully extended position or a ground contact member retraction stop configured to relieve tensile loads experienced by the first or second actuator due to loads applied to the associated ground contact element when the associated landing gear support is in a position between full up and full down.

9. The adaptive landing gear assembly of claim 1 , wherein:
the controller independently controls the first landing gear support and the second landing gear support in response to a human command.

10. The adaptive landing gear assembly of claim 9 , wherein:
the human command indicates landing on one or more of a flat surface, a sloped surface, a moving surface, a pitching surface, a rolling surface, and a surface attached to a ship.

11. The adaptive landing gear assembly of claim 1 , wherein:
the first landing gear support includes a first fluid chamber;
the second landing gear support includes a second fluid chamber; and
a hose fluidly couples the first fluid chamber to the second fluid chamber.

12. The adaptive landing gear assembly of claim 11 , further comprising:
one or more valves positioned in the hose, at the interface between the hose and the first fluid chamber, or at the interface between the hose and the second fluid chamber to control fluid flow between first fluid chamber and the second fluid chamber;
one or more of the controller and a control panel controlling the one or more valves.

13. The adaptive landing gear assembly of claim 1 , further comprising:
an actuator to position the first landing gear support in a position between fully up and fully down.

14. The adaptive landing gear assembly of claim 13 , wherein:
the actuator is electrically powered.

15. The adaptive landing gear assembly of claim 1 , wherein:
the first or second ground contact element is a skid.

16. The adaptive landing gear assembly of claim 15 , further comprising:
one or more skid assemblies, the one or more skid assemblies comprising the first landing gear support and the second landing gear support.

17. The adaptive landing gear assembly of claim 1 , wherein:
the sensor monitors one or more of engine health, aircraft vertical and horizontal velocities, rotor speed, aircraft gross weight, landing surface orientation, landing surface motion, human command, oscillations of an airframe of the aircraft, oscillations of a rotor system of the aircraft, orientation of the airframe, state of the first landing gear support, state of the first ground contact element, state of the second landing gear support, or state of the second ground contact element; and
the controller configured to determine that a landing is imminent in response to the sensor and terminate active control of the landing gear assembly and one of (i) maintain a current landing gear support state or (ii) control the first landing gear support and second landing gear support to establish one or more of a pre-defined stiffness and extension such that the anticipated landing loads may be absorbed by the first and second landing gear supports.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Waltner Peter James

Classifications

• B64C25/32

  characterised by elements which contact the ground or similar surface  (arrester hooks B64C25/68) · CPC title

• B64C25/10

  retractable, foldable, or the like · CPC title

• B64C25/60

  Oleo legs · CPC title

• B64C2025/325

  specially adapted for helicopters · CPC title

• B64C25/26

  Control or locking systems therefor · CPC title